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NASA/AMES A-03 AIRFOIL (ames03-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NASA/AMES A-03 AIRFOIL (ames03-il)
Reynolds number: 100,000
Max Cl/Cd: 34.42 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ames03-il-100000.txt
Download as CSV file: xf-ames03-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/AMES A-03 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4430   0.09734   0.09326  -0.0125   1.0000   0.1228
  -9.250  -0.4760   0.09194   0.08794  -0.0204   1.0000   0.1246
  -9.000  -0.5688   0.09756   0.09338  -0.0028   1.0000   0.1152
  -8.750  -0.5655   0.09325   0.08908  -0.0063   1.0000   0.1205
  -8.500  -0.6031   0.08614   0.08190  -0.0228   1.0000   0.1244
  -8.250  -0.5843   0.08136   0.07721  -0.0208   1.0000   0.1278
  -8.000  -0.5712   0.07823   0.07409  -0.0207   1.0000   0.1339
  -7.750  -0.6029   0.07290   0.06842  -0.0289   1.0000   0.1406
  -7.500  -0.5730   0.07003   0.06578  -0.0253   1.0000   0.1478
  -7.250  -0.6068   0.06736   0.06272  -0.0266   1.0000   0.1553
  -7.000  -0.5838   0.06428   0.05993  -0.0233   1.0000   0.1626
  -5.750  -0.5710   0.03821   0.03115  -0.0171   1.0000   0.0792
  -5.500  -0.5544   0.03461   0.02716  -0.0156   1.0000   0.0749
  -5.250  -0.5351   0.03159   0.02358  -0.0141   1.0000   0.0728
  -5.000  -0.5147   0.02975   0.02143  -0.0130   1.0000   0.0752
  -4.750  -0.4921   0.02778   0.01908  -0.0120   1.0000   0.0763
  -4.500  -0.4681   0.02599   0.01695  -0.0110   1.0000   0.0774
  -4.250  -0.4435   0.02463   0.01528  -0.0101   1.0000   0.0803
  -4.000  -0.4188   0.02314   0.01374  -0.0097   1.0000   0.0860
  -3.750  -0.3936   0.02208   0.01260  -0.0091   1.0000   0.0919
  -3.500  -0.3685   0.02095   0.01149  -0.0086   1.0000   0.1004
  -3.250  -0.3440   0.02003   0.01064  -0.0082   1.0000   0.1136
  -3.000  -0.3195   0.01912   0.00988  -0.0078   1.0000   0.1354
  -2.750  -0.2931   0.01762   0.00897  -0.0080   1.0000   0.2143
  -2.500  -0.2865   0.01531   0.00954  -0.0014   1.0000   0.8086
  -2.250  -0.2778   0.01567   0.00993   0.0048   1.0000   0.9022
  -2.000  -0.1668   0.01688   0.01071  -0.0083   1.0000   0.9925
  -1.750  -0.1334   0.01687   0.01050  -0.0107   1.0000   1.0000
  -1.500  -0.1314   0.01664   0.01017  -0.0073   1.0000   1.0000
  -1.250  -0.1269   0.01647   0.00988  -0.0042   1.0000   1.0000
  -1.000  -0.1182   0.01637   0.00966  -0.0018   1.0000   1.0000
  -0.750  -0.0859   0.01655   0.00968  -0.0037   0.9959   1.0000
  -0.500  -0.0227   0.01709   0.01005  -0.0113   0.9850   1.0000
  -0.250   0.0374   0.01756   0.01040  -0.0181   0.9738   1.0000
   0.000   0.1042   0.01801   0.01076  -0.0258   0.9599   1.0000
   0.250   0.1889   0.01828   0.01098  -0.0363   0.9422   1.0000
   0.500   0.2555   0.01839   0.01108  -0.0431   0.9267   1.0000
   0.750   0.2874   0.01857   0.01126  -0.0437   0.9140   1.0000
   1.000   0.3145   0.01872   0.01142  -0.0432   0.9008   1.0000
   1.250   0.3382   0.01881   0.01153  -0.0418   0.8867   1.0000
   1.500   0.3592   0.01881   0.01156  -0.0397   0.8718   1.0000
   1.750   0.3783   0.01868   0.01145  -0.0368   0.8560   1.0000
   2.000   0.3957   0.01838   0.01118  -0.0333   0.8397   1.0000
   2.250   0.4112   0.01789   0.01071  -0.0291   0.8227   1.0000
   2.500   0.4268   0.01729   0.01016  -0.0252   0.8003   1.0000
   2.750   0.4406   0.01628   0.00916  -0.0198   0.7779   1.0000
   3.000   0.4573   0.01517   0.00810  -0.0155   0.7369   1.0000
   3.250   0.4722   0.01387   0.00660  -0.0100   0.6039   1.0000
   3.500   0.4827   0.01442   0.00582  -0.0049   0.4478   1.0000
   3.750   0.5060   0.01527   0.00620  -0.0042   0.4021   1.0000
   4.000   0.5306   0.01596   0.00660  -0.0037   0.3776   1.0000
   4.250   0.5562   0.01659   0.00708  -0.0033   0.3591   1.0000
   4.500   0.5822   0.01723   0.00759  -0.0031   0.3435   1.0000
   4.750   0.6084   0.01793   0.00815  -0.0029   0.3305   1.0000
   5.000   0.6352   0.01858   0.00876  -0.0029   0.3181   1.0000
   5.250   0.6622   0.01926   0.00948  -0.0029   0.3064   1.0000
   5.500   0.6890   0.02003   0.01023  -0.0029   0.2959   1.0000
   5.750   0.7155   0.02089   0.01096  -0.0028   0.2858   1.0000
   6.000   0.7427   0.02158   0.01184  -0.0030   0.2750   1.0000
   6.250   0.7695   0.02246   0.01277  -0.0030   0.2648   1.0000
   6.500   0.7959   0.02341   0.01363  -0.0030   0.2550   1.0000
   6.750   0.8226   0.02418   0.01462  -0.0032   0.2440   1.0000
   7.000   0.8487   0.02515   0.01574  -0.0033   0.2333   1.0000
   7.250   0.8746   0.02615   0.01674  -0.0033   0.2232   1.0000
   7.500   0.9003   0.02696   0.01768  -0.0033   0.2118   1.0000
   7.750   0.9253   0.02795   0.01889  -0.0033   0.2000   1.0000
   8.000   0.9497   0.02885   0.01995  -0.0033   0.1881   1.0000
   8.250   0.9740   0.02958   0.02076  -0.0031   0.1763   1.0000
   8.500   0.9981   0.03004   0.02121  -0.0030   0.1641   1.0000
   8.750   1.0217   0.03037   0.02153  -0.0028   0.1514   1.0000
   9.000   1.0438   0.03078   0.02208  -0.0025   0.1380   1.0000
   9.250   1.0648   0.03129   0.02267  -0.0021   0.1246   1.0000
   9.500   1.0845   0.03207   0.02354  -0.0015   0.1115   1.0000
   9.750   1.1029   0.03329   0.02493  -0.0008   0.0996   1.0000
  10.000   1.1196   0.03497   0.02683   0.0000   0.0894   1.0000
  10.250   1.1358   0.03700   0.02902   0.0008   0.0818   1.0000
  10.500   1.1520   0.03888   0.03103   0.0017   0.0757   1.0000
  10.750   1.1641   0.04176   0.03414   0.0027   0.0711   1.0000
  11.000   1.1716   0.04435   0.03713   0.0040   0.0670   1.0000
  11.250   1.1823   0.04661   0.03951   0.0050   0.0638   1.0000
  11.500   1.1900   0.05070   0.04366   0.0059   0.0616   1.0000
  11.750   1.1802   0.05439   0.04786   0.0078   0.0609   1.0000
  12.000   1.1628   0.05820   0.05205   0.0098   0.0605   1.0000
  12.250   1.1411   0.06252   0.05670   0.0111   0.0604   1.0000
  12.500   1.1166   0.06757   0.06203   0.0112   0.0604   1.0000
  12.750   1.0896   0.07349   0.06818   0.0099   0.0607   1.0000
  13.000   1.0611   0.08048   0.07537   0.0071   0.0611   1.0000
  13.250   1.0318   0.08877   0.08380   0.0027   0.0616   1.0000
  13.500   0.8312   0.15255   0.14747  -0.0383   0.0971   1.0000
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